EP2244097A1 - Verfahren zur Verringerung des Einflusses von Satellitenfrequenzsprüngen auf ein globales Navigationsgerät - Google Patents

Verfahren zur Verringerung des Einflusses von Satellitenfrequenzsprüngen auf ein globales Navigationsgerät Download PDF

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Publication number
EP2244097A1
EP2244097A1 EP09005512A EP09005512A EP2244097A1 EP 2244097 A1 EP2244097 A1 EP 2244097A1 EP 09005512 A EP09005512 A EP 09005512A EP 09005512 A EP09005512 A EP 09005512A EP 2244097 A1 EP2244097 A1 EP 2244097A1
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European Patent Office
Prior art keywords
space vehicles
space
navigation signals
navigation
group
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EP09005512A
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English (en)
French (fr)
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EP2244097B1 (de
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Veit Dr. Oehler
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Airbus DS GmbH
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Astrium GmbH
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Priority to EP12007983A priority Critical patent/EP2565675A1/de
Priority to ES09005512.0T priority patent/ES2461093T3/es
Priority to EP09005512.0A priority patent/EP2244097B1/de
Priority to US12/763,855 priority patent/US8570217B2/en
Publication of EP2244097A1 publication Critical patent/EP2244097A1/de
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    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01S—RADIO DIRECTION-FINDING; RADIO NAVIGATION; DETERMINING DISTANCE OR VELOCITY BY USE OF RADIO WAVES; LOCATING OR PRESENCE-DETECTING BY USE OF THE REFLECTION OR RERADIATION OF RADIO WAVES; ANALOGOUS ARRANGEMENTS USING OTHER WAVES
    • G01S19/00—Satellite radio beacon positioning systems; Determining position, velocity or attitude using signals transmitted by such systems
    • G01S19/01—Satellite radio beacon positioning systems transmitting time-stamped messages, e.g. GPS [Global Positioning System], GLONASS [Global Orbiting Navigation Satellite System] or GALILEO
    • G01S19/13—Receivers
    • G01S19/20—Integrity monitoring, fault detection or fault isolation of space segment
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01S—RADIO DIRECTION-FINDING; RADIO NAVIGATION; DETERMINING DISTANCE OR VELOCITY BY USE OF RADIO WAVES; LOCATING OR PRESENCE-DETECTING BY USE OF THE REFLECTION OR RERADIATION OF RADIO WAVES; ANALOGOUS ARRANGEMENTS USING OTHER WAVES
    • G01S19/00—Satellite radio beacon positioning systems; Determining position, velocity or attitude using signals transmitted by such systems
    • G01S19/01—Satellite radio beacon positioning systems transmitting time-stamped messages, e.g. GPS [Global Positioning System], GLONASS [Global Orbiting Navigation Satellite System] or GALILEO
    • G01S19/13—Receivers
    • G01S19/24—Acquisition or tracking or demodulation of signals transmitted by the system
    • G01S19/28—Satellite selection
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01S—RADIO DIRECTION-FINDING; RADIO NAVIGATION; DETERMINING DISTANCE OR VELOCITY BY USE OF RADIO WAVES; LOCATING OR PRESENCE-DETECTING BY USE OF THE REFLECTION OR RERADIATION OF RADIO WAVES; ANALOGOUS ARRANGEMENTS USING OTHER WAVES
    • G01S19/00—Satellite radio beacon positioning systems; Determining position, velocity or attitude using signals transmitted by such systems
    • G01S19/01—Satellite radio beacon positioning systems transmitting time-stamped messages, e.g. GPS [Global Positioning System], GLONASS [Global Orbiting Navigation Satellite System] or GALILEO
    • G01S19/13—Receivers
    • G01S19/33—Multimode operation in different systems which transmit time stamped messages, e.g. GPS/GLONASS

Definitions

  • the present invention is directed to a method of amending navigation data of a global navigation system, which comprises several space vehicles transmitting information to a device for position detection, each space vehicle comprising at least one clock, wherein the impact of space vehicle clock frequency jumps on the device for position detection is reduced.
  • WO 2006/032422 A1 discloses a method and apparatus for providing integrity information for users of a global navigation system. The disclosure of this document is fully incorporated by reference into the present application.
  • the respective integrity risk calculated for all combinations of the navigation signals received from the space vehicles of said first group of space vehicles and of said second group of space vehicles needs to be lower than the predetermined allocated integrity risk because it is unknown whether one of the signals received from said second group of space vehicles (and if so, which one) just underlied a frequency jump or will underlie it in the near future. Only such a procedure considering all combinations will deliver an integer (i.e, safe) result.
  • the core idea of the first inventive solution is thus to primarily consider signals from not jumping satellite clock sources.
  • the effect of satellite clock frequency jumps and other similar events is thus reduced, if such events cannot be avoided at satellite level, or detected at ground segment level with removal at user level through transmitted alerts, by avoiding the use of affected satellites at user level according to the method steps of claim 1.
  • This can be realized through suitable user algorithm modifications.
  • This inventive approach would limit the impact on the projects Galileo In Orbit Validation (IOV) and the Full Operational Constellation (FOC) to a minium, since neither space segment design changes nor ground segment modifications are required which typically significantly impact cost and schedule. Only additional analyses and concept modifications at system level are required together with the relevant test user updates, which are not affecting the related mentioned projects significantly.
  • the basic idea of the invention is thus to overcome at user algorithm level the problem that small errors in the order of a few meters, which are imposed by e.g. satellite clock frequency jumps, can neither be avoided at satellite level, nor be detected by the Galileo ground integrity monitoring concept, This is done by related user integrity algorithm modifications that try to avoid to a maximum extent the usage of possibly affected signals, respectively only consider such signals that would have acceptable impact at user level from integrity service availability point of view.
  • Those modified user algorithms do not require for significant system, space or ground segment design changes, since only the final user algorithm implementation is affected.
  • minor data dissemination adjustments i.e. updates of the signal-in-space interface control document [SIS-ICD]
  • SIS-ICD signal-in-space interface control document
  • the navigation signals received from a space vehicle of said second group of space vehicles are added to the navigation signals in an integer and safe way by putting them to the ground segment detection threshold in step 1e).
  • the ground detection threshold represents the smallest error, i.e. jump for said second group of space vehicles, that the ground integrity monitoring function is able to detect and to send a warning to the user immediately.
  • Putting the navigation signal to said threshold means to consider the signal and the related integrity information fully affected by a jump or other error source up to the detection threshold, which ensures the integer consideration of said signal, since it is assumed that a jump occurred with maximum possible error that is just not detected by the ground segment.
  • the navigation signals received from a space vehicle of said second group of space vehicles are added to the navigation signals in an integer and safe way by inflating the integrity information of the signal in space accuracy (SISA) in step 1e) to ensure integer overbounding of the real signal in space error of said signal by the used inflated SISA information.
  • SISA space accuracy
  • Inflafing the integrity information of the signal means that SISA is inflated in such a way, that this integrity information is still properly (i.e. integer) overbounding the real error even if the signal has just jumped.
  • the inflation needs to be done in a way that even the worst possible jump magnitude (i.e, maximum error) is covered.
  • Such alternative approach could be considered if the SISA inflation provides better integrity service availability compared to the above described conservative detection threshold approach, and vice-versa.
  • the SISA is inflated as a function of navigation data age in order to reduce the required integrity information inflation of said signal.
  • the effect of the jump and the related imposed error increases with the age of the latest received satellite clock parameters that are used to model the satellite clock behaviour.
  • the "old” parameter still fit the new (after the jump) clock behaviour, and only after some time the real clock drifts away from the estimated (modelled) clock behaviour and the imposed error increases accordingly. If only signals with "young" navigation data (which carry also the clock parameters) are considered, the SISA does not need to be inflated to cover the worst possible maximum error, but only to cover the maximum error that could occur according to the navigation data age.
  • the space vehicles of said first group of space vehicles are provided with clocks working according to the principle of passive hydrogen maser (PHM). These PHM clocks are known as not having frequency jumps.
  • PHM passive hydrogen maser
  • the core idea of the second inventive solution is to only consider combinations of measurements that would allow for service usage even in safe consideration of jumping signals.
  • the navigation signals received from each of the space vehicles of the combination are added to the navigation signals in an integer and safe way by putting them to the ground segment detection threshold in step 6f).
  • the navigation signals received from each of the space vehicles of the combination are added to the navigation signals in an integer and safe way by inflating the integrity information of the signal in space accuracy (SISA) in step 6f) to ensure integer overbounding of the real signal in space error of said signal by the used inflated SISA information.
  • SISA space accuracy
  • the SISA is inflated as a function of navigation data age in order to reduce the required integrity information inflation of said signal.
  • Galileo which will be an independent, global European controlled satellite-based navigation system.
  • the Galileo Global Component will comprise a constellation of satellites monitored and controlled by a Ground Segment which will also provide the capability to detect satellite or system malfunctions and broadcast real-time warnings, so called integrity messages, to users.
  • the Galileo Global Component will provide a number of satellite-only navigation services:
  • Galileo System will provide Local Services to improve performances (e.g. integrity) on a local basis.
  • the Galileo system will also provide support to Search-and-Rescue (SAR) services,
  • Galileo will support External Regional Integrity Services (ERIS) by disseminating, over selected Galileo satellites, integrity data generated by independent, external regional integrity service providers.
  • ERIS External Regional Integrity Services
  • the Galileo Space Segment will comprise a constellation of 27 operational satellites plus three in-orbit (inactive) spare satellites in medium-Earth orbit (MEO). Each operational satellite will broadcast a set of navigation signals carrying clock synchronisation, ephemeris, integrity and other data, depending on the particular signal. A user equipped with a suitable receiver with good visibility of the sky will be able to receive around 11 Galileo satellites to determine his position to within a few meters.
  • the Galileo Ground Segment will control the complete Galileo constellation, monitor the satellite health, and upload data for subsequent broadcast to users via the mission uplink stations (ULS).
  • the key elements of these data such as clock synchronisation, ephemeris and integrity messages will be calculated from measurements made by a worldwide network of Galileo Sensor Stations (GSS).
  • Satellite navigation systems strongly depend on the predictability of the used onboard satellite clocks and their performance, since such predictability directly drives the related service performance, e.g. in terms of positioning accuracy and thus service availability, If such performance is degraded by not predictable events like onboard satellite clock frequency jumps, this degrades the finally achievable service performance at user level.
  • SISA signals-in-space accuracy
  • the present invention proposes methods how to recover from such effect at user algorithm level, to limit the impact of satellite clock frequency jumps on the Galileo services.
  • Rubidium clock jump characteristic needs to be considered as normal behaviour, rather than a rare feared event.
  • Such effect is also commonly known for longer testes navigation satellites, like the GPS satellites.
  • the signals of the PHM (master) performance do not show any jumps, and should therefore be preferred at user level.
  • Fig. 1 presents the maximum prediction error in the range domain depending on the jump magnitude and navigation message update rate and age of the message, respectively.
  • the imposed range error decreases significantly, i.e. the age of the navigation message should also be considered at user level.
  • the received SISA for the relevant satellite can be used as standard deviation a, and the applicable onboard clock frequency jump barrier threshold as bias b (either received for the specific satellite via the navigation message, or hard defined also within the receiver),
  • Fig. 2 illustrates SISA inflation for 85cm standard deviation (received SISA) for different biases up to typical 2 meters.
  • the inflated SISA would correspond to a value of around 1.7 meters, two times higher than the 85cm SISA upper bound specification that is required to globally achieve integrity service performance,
  • the maximum prediction errors would need to be smaller than around 50cm to 100cm to not degrade the SISA performance too much, which might jeopardize the Galileo integrity services performance.
  • the signal selection could also be done with SISA threshold, depending on the final Galileo PHM performance compared to RAFS. With typically around 20cm (>25%) improved performance for PHM frequency standard, the additional SIS-ICD information might not be necessarily required and the user just picks from available signals with SISA below such threshold (e.g, 65cm). Furthermore the Rubidium-clock frequency jumps will also further increase the underlying historical SISA value for the RAFS statistics, which further increases the difference between PHM and RAFS SISA and reduces the test and threshold ambiguity.
  • FIG. 3 illustrates the general algorithm function with known signal frequency standard source:
  • RAFS signal If more than one RAFS signal is added, then only a certain number of RAFS signals (called “sub-set”) need to be degraded (i.e. put to threshold or with inflated SISA), since the probability to have more than one (or two, three, ...) RAFS signal simultaneously affected by a jump is negligible, respectively is already covered in the system integrity allocations.
  • sub-set a certain number of RAFS signals
  • the different options which RAFS signals are considered (i.e, added) are called "combinations”.
  • the algorithm tries to start with a certain set of optimum signals (A), that need to be put to the threshold respectively inflated according to the already described process (B), and starts to add signals with higher risk contributions if the service is not yet available (D). If for one combination all subsets allow to start or continue a critical operation (C), no additional signals are required.
  • the invention describes a method how to minimize the impact of satellite clock frequency jumps and other similar causes on Galileo's integrity services, by only modifying the user algorithm. Additional information could further be provided via updated messages (i.e. SIS-ICD update) to improve the concepts, but is not necessarily required.
  • updated messages i.e. SIS-ICD update
  • the invention ensures a valid, but now also feasible Galileo integrity service from availability point of view, without significant changes at Space or Ground Segment level. Only minor changes at System and TUS level are required,

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  • Engineering & Computer Science (AREA)
  • Radar, Positioning & Navigation (AREA)
  • Remote Sensing (AREA)
  • Computer Networks & Wireless Communication (AREA)
  • Physics & Mathematics (AREA)
  • General Physics & Mathematics (AREA)
  • Computer Security & Cryptography (AREA)
  • Position Fixing By Use Of Radio Waves (AREA)
EP09005512.0A 2009-04-20 2009-04-20 Verfahren zur Verringerung des Einflusses von Satellitenfrequenzsprüngen auf ein globales Navigationsgerät Not-in-force EP2244097B1 (de)

Priority Applications (4)

Application Number Priority Date Filing Date Title
EP12007983A EP2565675A1 (de) 2009-04-20 2009-04-20 Verfahren zur Verringerung des Einflusses von Satellitenfrequenzsprüngen auf ein globales Navigationsgerät
ES09005512.0T ES2461093T3 (es) 2009-04-20 2009-04-20 Un método de reducción del impacto de los saltos de frecuencia de vehículos espaciales sobre un dispositivo de navegación global
EP09005512.0A EP2244097B1 (de) 2009-04-20 2009-04-20 Verfahren zur Verringerung des Einflusses von Satellitenfrequenzsprüngen auf ein globales Navigationsgerät
US12/763,855 US8570217B2 (en) 2009-04-20 2010-04-20 Method of amending navigation data of a global navigation system

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Application Number Priority Date Filing Date Title
EP09005512.0A EP2244097B1 (de) 2009-04-20 2009-04-20 Verfahren zur Verringerung des Einflusses von Satellitenfrequenzsprüngen auf ein globales Navigationsgerät

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EP12007983A Ceased EP2565675A1 (de) 2009-04-20 2009-04-20 Verfahren zur Verringerung des Einflusses von Satellitenfrequenzsprüngen auf ein globales Navigationsgerät

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WO2014042757A1 (en) * 2012-09-12 2014-03-20 Raytheon Company Maintaining integrity against erroneous ephemeris
US9829582B2 (en) 2011-09-19 2017-11-28 Raytheon Company Method and apparatus for differential global positioning system (DGPS)-based real time attitude determination (RTAD)
US10114126B2 (en) 2015-04-30 2018-10-30 Raytheon Company Sensor installation monitoring
EP3499270A1 (de) * 2017-12-13 2019-06-19 Airbus Defence and Space GmbH Verwendung eines dynamischen signalqualitätsindikatormodells zum batteriesparen
US10551196B2 (en) 2015-04-30 2020-02-04 Raytheon Company Sensor installation monitoring

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EP2461182B1 (de) * 2010-12-01 2014-06-04 European Space Agency Verfahren und Vorrichtung zur Bestimmung eines Integritätsanzeigeparameters zum Anzeigen der Integrität von in einem globalen Positionierungssystem bestimmten Positionierungsinformationen
EP2930534A1 (de) * 2014-04-11 2015-10-14 Astrium GmbH Verfahren zur Verringerung der Auswirkungen von Signalanomalien auf eine Vorrichtung zur Positionsbestimmung in einem globalen Navigationssystem
CN105467406B (zh) * 2015-12-18 2017-10-24 中国科学院测量与地球物理研究所 多测站广播星历确定用户测距精度上界值的方法
US10760911B2 (en) * 2017-03-29 2020-09-01 Honeywell International Inc. Integrity monitoring method for navigation systems with heterogeneous measurements
DE102017111091B4 (de) * 2017-05-22 2019-01-10 Deutsches Zentrum für Luft- und Raumfahrt e.V. Satellitensystem für die Navigation und/oder die Geodäsie
US10935663B2 (en) * 2017-09-22 2021-03-02 Qualcomm Incorporated Satellite integrity monitoring with crowdsourced mobile device data
CN109756260B (zh) * 2018-11-23 2021-03-02 中国西安卫星测控中心 一种量子卫星上行数传系统及其自动操控方法
CN110687555B (zh) * 2019-09-23 2022-03-04 西安空间无线电技术研究所 一种导航卫星原子钟弱频率跳变在轨自主快速检测方法
CN111967210B (zh) * 2020-07-03 2023-06-06 北京空间飞行器总体设计部 一种针对导航下行信号功能中断的phm设计方法

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US9829582B2 (en) 2011-09-19 2017-11-28 Raytheon Company Method and apparatus for differential global positioning system (DGPS)-based real time attitude determination (RTAD)
WO2014042757A1 (en) * 2012-09-12 2014-03-20 Raytheon Company Maintaining integrity against erroneous ephemeris
US10114126B2 (en) 2015-04-30 2018-10-30 Raytheon Company Sensor installation monitoring
US10551196B2 (en) 2015-04-30 2020-02-04 Raytheon Company Sensor installation monitoring
EP3499270A1 (de) * 2017-12-13 2019-06-19 Airbus Defence and Space GmbH Verwendung eines dynamischen signalqualitätsindikatormodells zum batteriesparen
WO2019115293A1 (en) * 2017-12-13 2019-06-20 Airbus Defence and Space GmbH Use of a dynamic signal quality indicator model for battery saving

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US8570217B2 (en) 2013-10-29
ES2461093T3 (es) 2014-05-16
US20100265132A1 (en) 2010-10-21
EP2244097B1 (de) 2014-02-26
EP2565675A1 (de) 2013-03-06

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